Earth Re-entry CubeSat Mission Attitude Control Simulation and Mission Analysis

摘要

With the popular development of CubeSats there are more and more different applications for them Re-entry mission is one of the critical parts of earth observation Re-entry CubeSat can carry the scientific equipment which can record some measurements during Re-entry phase in order to increase the knowledge of the properties of atmosphere This research is referred to this kind of mission approach with a 3U CubeSat In order to reach the objective attitude determination and control subsystem is required to perform attitude stabilization and pointing control This research describes the mission analysis and development of attitude determination and control subsystem for the CubeSat with emphasis on the operation and control strategy Moreover the attitude determination and control subsystem will not be activated during the re-entry since the ADCS hardware cannot sustain under such extreme scenario like supersonic speed and extremely high temperature But the design of hardware and structure still affect the satellite operation during orbital cruise Because of the thermal consideration the use of the sensors are limited Moreover the design of the deployable solar panels which are responsible for performing aerodynamic stability for re-entry phase will also be investigated in particular the deployment strategy is assessed Software-in-the-loop simulation is used for mission design and performance analysis A simulation software has been built up based on MATLAB/Simulink which contains the dynamic model of the satellite sensor/actuator model environment model attitude controller and estimator With the design of simulation software we can get several results from different combination of controller and estimator The performance of the results can help the designer to define the operation strategy and identify the threshold of operation Also the software can simulate the error setting to observe the behavior of satellite this can help ground operation to identify the possible error condition in real mission The simulation of de-orbit scenario will take attitude control into consideration it can estimate the orbital lifetime to see whether it meets the mission requirement or not In conclusion the simulation tool not only helps us to design ADCS and makes the mission planning but also provides an insight into the operating strategy

獎項日期	2017 8月 15
原文	English
監督員	Jiun-Jih Miau (Supervisor)